(2)
Connect torque tubes to coupling on transmission assembly. Lockwire heads of torque tube screws together.
(3)
Remove plug screws and attach flap rigging tool at location marked by black arrows at WBL 228.5 or hand position outboard flap rigging beam to black stripes located at WBL
228.5 on front and rear spar (Section A-A, Fig. 501).
NOTE: If black stripes are not on airplane, stencil 0.25 inch wide stripes per tool drawing F80209.
If shim between carriage bearing support and midflap has been lost or altered so that it is impossible to determine shim thickness on flap that was removed, both outboard flaps must be rigged per the following procedure. This procedure locates flap trailing edge relative to wing chord plane and requires the use of flap rigging tool.
567
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-72 Page 501
G42469
Outboard Trailing Edge Flap Positioning 500
27-51-72 Figure 501 (Sheet 1) Feb 20/90
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Outboard Trailing Edge Flap Positioning
May 01/01 Figure 501 (Sheet 2) 27-51-72
Page 502A
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4) Apply 30 pound upward force against a minimum 4.0 by 6.0-inch aluminum plate at aft edge of aftflap near the aftflap track rollers to hold aftflap in retracted position and measure flap position at flap rigging tool and fixed rib at outboard end of flap. Check that aftflap trailing edge is 0.00 to 0.25 inch below wing chord plane with aftflap airload rollers contacting flap track. Check that flap is symmetrical within 0.10 inch of opposite flap wing chord plane alignment.
NOTE: If this dimension cannot be achieved without exceeding the 0.23-inch maximum allowable shim thickness, use a 0.23-inch shim regardless of the flap position relative to the wing chord. If you have made trim corrections with the outboard TE flaps, the dimension can be more than the 0.00 to 0.25-inch limit.
The aftflap is in the retracted position when the clearance between the lower trailing edge of the midflap and the leading edge of the aftflap is 0.00 to 0.13 inch for the full length of the aftflap.
(5)
If flap trailing edge is not within limits, refer to chart (Fig. 501) and determine shim thickness required to position aftflap trailing edge 0.00 to 0.25 inch below wing chord plane. Inboard and outboard carriage shims should be equal within 0.12 inch.
(6)
Remove access panels from upper surface of midflap and remove bolts attaching carriage bearing support to midflap forging (Fig. 503).
(7)
Position carriage bearing support over end of flap carriage with correct shim thickness installed between carriage support and midflap forging, install bolt with washer and nut. Tighten 3/8-inch nut 160 to 190 pound-inches. Tighten 5/16-inch nut 100 to 140 pound-inches.
(8)
Remove outboard flap rigging tool and install plug screws if required (Fig. 501).
500
27-51-72 Page 502B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/91
CAUTION: SHIM THICKNESS ADJUSTMENT BETWEEN MIDFLAP CARRIAGE BEARING SUPPORT AND MIDFLAP FORGING CHANGES PRELOAD CUP ADJUSTMENT. INCORRECT ADJUSTMENT COULD CAUSE DAMAGE TO PRELOAD CUP.
NOTE: Shim or tapered filler thickness between leaf spring and midflap should be changed when shim thickness between carriage bearing support and midflap is changed (i.e., remove same shim thickness above leaf spring as was added under carriage bearing support).
(8a) If shim thickness between carriage bearing support and midflap has been changed, re-adjust leaf spring deflection as required per step 1.C.(17).
(9)
Provide system A hydraulic power (Ref 27-51-0).
(10)
Position flap control lever to FLAP DOWN (40-unit) detent to lower flaps, then to FLAP UP detent to retract flaps to normal up position. The ballscrew nut upstop must stop in the range of 170 to 190 degrees (1/2 turn ±10 degrees) turns from contact at FLAP UP position. Check dimension X (Fig. 504).
CAUTION: THE MAXIMUM ALLOWABLE ANGULAR CLEARANCE IS 1/4 TO 5/6 TURNS IF LATERAL TRIM CORRECTION HAS BEEN MADE. A VALUE FOR (X) OUTSIDE THIS RANGE MAY CAUSE DAMAGE DURING FLAP OPERATION. PREVIOUS LATERAL TRIM CORRECTIONS SHOULD BE RETAINED.
500
Feb 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-72 Page 503
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(22)
